EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 1230 AIRFOIL (e1230-il) Reynolds number: 100,000 Max Cl/Cd: 35.79 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1230-il-100000.txt Download as CSV file: xf-e1230-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1230 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4282 0.09708 0.09277 -0.0490 1.0000 0.1440
-9.250 -0.4156 0.07834 0.07396 -0.0532 1.0000 0.0914
-9.000 -0.5341 0.06865 0.06411 -0.0513 1.0000 0.0751
-8.750 -0.6393 0.06266 0.05747 -0.0425 1.0000 0.0675
-8.500 -0.6177 0.06173 0.05696 -0.0414 1.0000 0.0695
-8.250 -0.6407 0.05752 0.05241 -0.0385 0.9982 0.0660
-8.000 -0.6191 0.05107 0.04546 -0.0430 0.9883 0.0639
-7.750 -0.5958 0.04493 0.03858 -0.0464 0.9781 0.0625
-7.500 -0.5642 0.04073 0.03380 -0.0492 0.9678 0.0632
-7.250 -0.5306 0.03764 0.03009 -0.0516 0.9562 0.0662
-7.000 -0.4918 0.03486 0.02699 -0.0545 0.9461 0.0697
-6.750 -0.4527 0.03278 0.02473 -0.0567 0.9346 0.0735
-6.500 -0.4144 0.03061 0.02229 -0.0587 0.9229 0.0792
-6.250 -0.3728 0.02904 0.02049 -0.0611 0.9121 0.0881
-6.000 -0.3256 0.02706 0.01855 -0.0645 0.9043 0.1009
-5.750 -0.2863 0.02544 0.01707 -0.0665 0.8925 0.1173
-5.500 -0.2373 0.02391 0.01552 -0.0701 0.8854 0.1432
-5.250 -0.2029 0.02257 0.01439 -0.0713 0.8708 0.1671
-5.000 -0.1673 0.02151 0.01334 -0.0724 0.8562 0.1957
-4.750 -0.1330 0.02032 0.01239 -0.0734 0.8418 0.2296
-4.500 -0.1023 0.01909 0.01149 -0.0737 0.8271 0.2797
-4.250 -0.0829 0.01767 0.01082 -0.0720 0.8115 0.3922
-4.000 -0.0681 0.01760 0.01154 -0.0679 0.7943 0.5647
-3.750 -0.0449 0.01831 0.01211 -0.0654 0.7773 0.6279
-3.500 -0.0215 0.01885 0.01246 -0.0630 0.7612 0.6644
-3.250 0.0031 0.01916 0.01262 -0.0610 0.7462 0.6920
-3.000 0.0295 0.01937 0.01266 -0.0592 0.7327 0.7166
-2.750 0.0504 0.01951 0.01270 -0.0568 0.7173 0.7378
-2.500 0.0733 0.01966 0.01276 -0.0546 0.7031 0.7567
-2.250 0.0986 0.01980 0.01275 -0.0528 0.6906 0.7751
-2.000 0.1222 0.01992 0.01275 -0.0508 0.6776 0.7927
-1.750 0.1445 0.02008 0.01283 -0.0487 0.6647 0.8100
-1.500 0.1722 0.02028 0.01285 -0.0472 0.6540 0.8282
-1.250 0.1960 0.02049 0.01300 -0.0453 0.6412 0.8457
-1.000 0.2256 0.02074 0.01311 -0.0445 0.6298 0.8612
-0.750 0.2596 0.02091 0.01311 -0.0449 0.6188 0.8731
-0.500 0.2881 0.02106 0.01317 -0.0449 0.6075 0.8836
-0.250 0.3190 0.02110 0.01300 -0.0453 0.5983 0.8932
0.000 0.3423 0.02118 0.01305 -0.0447 0.5874 0.9031
0.250 0.3862 0.02131 0.01292 -0.0476 0.5782 0.9088
0.500 0.4115 0.02143 0.01305 -0.0476 0.5675 0.9174
0.750 0.4545 0.02156 0.01296 -0.0506 0.5593 0.9227
1.000 0.4813 0.02174 0.01316 -0.0509 0.5494 0.9307
1.250 0.5237 0.02185 0.01307 -0.0539 0.5411 0.9357
1.500 0.5513 0.02208 0.01332 -0.0546 0.5321 0.9436
1.750 0.5931 0.02223 0.01334 -0.0576 0.5240 0.9488
2.000 0.6234 0.02251 0.01356 -0.0588 0.5169 0.9562
2.250 0.6631 0.02274 0.01378 -0.0617 0.5082 0.9619
2.500 0.7000 0.02292 0.01375 -0.0639 0.5021 0.9690
2.750 0.7353 0.02330 0.01425 -0.0663 0.4934 0.9754
3.000 0.7726 0.02352 0.01440 -0.0688 0.4869 0.9826
3.250 0.8133 0.02388 0.01467 -0.0720 0.4809 0.9894
3.500 0.8488 0.02431 0.01521 -0.0747 0.4732 0.9972
3.750 0.8741 0.02454 0.01537 -0.0750 0.4678 1.0000
4.000 0.8897 0.02486 0.01558 -0.0736 0.4638 1.0000
4.250 0.8835 0.02540 0.01631 -0.0689 0.4588 1.0000
4.500 0.8816 0.02584 0.01680 -0.0647 0.4544 1.0000
4.750 0.8961 0.02625 0.01714 -0.0629 0.4502 1.0000
5.000 0.9207 0.02666 0.01738 -0.0626 0.4464 1.0000
5.250 0.9278 0.02761 0.01846 -0.0597 0.4411 1.0000
5.500 0.9429 0.02835 0.01925 -0.0580 0.4358 1.0000
5.750 0.9663 0.02883 0.01968 -0.0575 0.4315 1.0000
6.000 0.9949 0.02932 0.02005 -0.0578 0.4280 1.0000
6.250 1.0015 0.03064 0.02155 -0.0550 0.4234 1.0000
6.500 1.0124 0.03177 0.02281 -0.0530 0.4184 1.0000
6.750 1.0347 0.03238 0.02341 -0.0523 0.4142 1.0000
7.000 1.0649 0.03274 0.02367 -0.0528 0.4107 1.0000
7.250 1.0754 0.03413 0.02518 -0.0508 0.4067 1.0000
7.500 1.0709 0.03620 0.02749 -0.0472 0.4018 1.0000
7.750 1.0833 0.03745 0.02882 -0.0456 0.3978 1.0000
8.000 1.1111 0.03788 0.02921 -0.0457 0.3944 1.0000
8.250 1.1482 0.03806 0.02929 -0.0470 0.3914 1.0000
8.500 1.1015 0.04249 0.03414 -0.0393 0.3859 1.0000
8.750 0.9390 0.05656 0.04859 -0.0274 0.3767 1.0000
9.000 1.0341 0.05088 0.04282 -0.0293 0.3767 1.0000
9.250 1.1211 0.04761 0.03945 -0.0338 0.3752 1.0000
10.750 0.6168 0.12863 0.12115 -0.0449 0.3815 1.0000
11.000 0.6379 0.13071 0.12325 -0.0450 0.3767 1.0000
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Polar data table (+)
Polar graphs
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